What is the minimum energy required to launch a satellite of mass m from the surface of a planet of mass M and radius R in a circular orbit at an altitude of 2R?

Question

( A ) $\frac{2 G m M}{3R}$
( B ) $\frac{G m M}{3R}$
( C ) $\frac{G m M}{2R}$
( D ) $\frac{5 G m M}{6R}$